TY - JOUR
T1 - Fracture Analysis for Damaged Aircraft Fuselage Subjected to Blast
AU - Ju, Jin San
AU - Jiang, Xiu Gen
AU - Fu, Xiang Rong
JF - Key Engineering Materials
VL - 348-349
SP - 705
EP - 708
SN - 1662-9795
PY - 2007
PB - Trans Tech Publications
DO - 10.4028/www.scientific.net/KEM.348-349.705
UR - https://www.scientific.net/KEM.348-349.705
KW - Blast Load
KW - Crack
KW - Dynamic Stress Intensity Factor (DSIF)
KW - Fracture Analysis
KW - Fuselage
AB - This paper primarily presents the development and application of automation
computational analysis techniques to determine the dynamic stress intensity factor for the damaged
aircraft fuselage subjected to triangle blast load. A program based on automated procedure to
simulate cracked fuselage is developed. It may create 3-dimention panel model using
parameterization. The stress around the crack tips will be captured and the dynamic stress intensity
factor can be obtained at every moment of the blast automatically. A typical curved panel model
which consists of 7 frames and 8 stringers is calculated. The calculation results shown that the form
of the dynamic SIF curve is similar to that of the triangle load curve while the peak point of
dynamic SIF curve occurs a little later than that of the load curve due to the inertia effect. The
longer the crack is, the more obvious the effect is. The peak SIF value of the crack under blast load
is bigger than that under the static load for certain crack length. The longer the crack is, the bigger
the difference between the dynamic peak SIF value and static SIF is. At the same time, the load
time has effect on the dynamic SIF curve and its peak value. These results show good agreements
with theoretical principles.
ER -